Launching device



July 22, 1958 c. RE ETAL LAUNCHING DEVICE 5- Sheets-Sheet 2 Filed April16, 1954 m m gm 8 wmn mmm mg .WMI; KN HEM TEENRyT M .m gm, wm m MDLMMWMW July 22, 1958 c. RE ETAL 2,844,073

LAUNCHING DEVICE Filed April 16, 1954 s Sheets-Sheet 3 93 in. -="-K C 024 1 00 l 2/ In 74 .4431 7/ 7: ea zn 7 164 l. if .15

Fin/.41. If {i VVVV I 6 In. 11;

.4 i3 A 1,1 I? .154

m M i W 2! r4 g-m1 1611. GAR/VETT C. DUNCAN,

DAN/El. KIND 2 vvvv V LEIGH E SIR/(EL Alva .6512 CARLO PE GEORGE F. RICE8 VICTOR 7- KOOZ/N;

INVENTORS- HUEBNER, BEEHLER, WOPRE L 8 HERZ/G,

E ATTORNEYS.

United States Patent LAUNCHIN G DEVICE Carlo R, George F. Rice, andLeigh F. Birkeland, Van Nuys, Victor T. Koozin, Woodland Hills, GarnettC. Duncan, Glendale, and Daniel Kinda, Torrance, Calif., assignors, bymesne assignments, to Royal Industries, Inc., Alhambra, Calif., acorporation of California Application April 16, 1954, Serial No. 423,618

6 Claims. (Cl. 89--1.7)

The invention relates to military Weapons and has particular referenceto a launching device by means of which a plurality of missiles in thenature of rockets can be launched simultaneouslyand preferablyin closesequence one after the other in a manner known generally as ripple fire.The launching device is one designed to be'carried by aircraft or othervehicles by use of racks or pylons.

Since the employment of rockets as missiles to be launched fromairplanes hasbecome prevalent, a variety of devices have beenconstructed to facilitate the launching of missiles of this kind.Practice has dictated that launchers be capable of launching a series ofsuch rockets with each aiming of the launcher. Increased accuracy hasbeen found possible of attainment when the rockets are launched in arapid sequence, one shortly in advance of the other, so that the rocketsstream from the launcher in a continuous stream until the last rockethas been loosed.

Inasmuch as these launchers are customarily carried on the wings of theairplane, it has been found highly advantageous to construct thelaunchersof such material that the launchers can be jettisoned after therockets have been fired so as to permit the airplane to return to thebase clean.

Launchers heretofore designed have been of metallic construction buteven when attempted to be made of relatively light-weight metals and ofgenerally light-weight construction they have nevertheless beendesigned, manufactured and. used as relatively expensive permanentequipment.

It is therefore among the objects of the invention to provide a new andimproved inexpensive, disposable rocket launching device which isdependable to the ex- 7 tent required of such weapons.

Another object of the invention is to provide a new and improveddisposable rocket launching device which is constructed of exceptionallyinexpensive and expendable material in the nature of paper, plastics,cellulose, and likematerial, while at the same time having built intothe launcher sufficient strength and rigidity to be carried aloft undervirtually all conditions which might be encountered in warfare of thesort to which it is adapted.

Another object of the invention is to provide a new and improvedinexpensive, disposable rocket launching device which can, if need be,be employed as a means of shipping rockets, the device having removablefairings both fore and aft which can be attached to the main body of thedeviceafter. it is in place on an airplane, thereby to streamline thedevice for effective flying, the streamlined fairings being frangible tothe extent-that they are readily broken open when the rockets are fired.

Still another object of the invention is to provide" a new and improvedlaunching device for a plurality of rockets which include a detent orcatch device capable of easily released manually in the event it mightbecome necessary to unload the rockets without their being fired.

Still another object of the invention is to provide a new and improvedelectric actuated firing mechanism which is very accurately timed tofire a series of rockets in a predetermined sequence, commonlyidentified as ripple firing, the electric mechanism beingcompact,.accurate, dependable, operable in response to a relatively lowcurrent, and so arranged that it can be located compactly adjacent theaft ends of the rockets without increasing or otherwise burdening therocket mountings.

With these and other objects in view, the invention consists in theconstruction, arrangement and combination of the various parts of thedevice wherebythe objects contemplated are attained, as hereinafter setforth, pointed Figure l is a perspective view of the rocket launchingdevice shown in the position itwould have when attached to the undersideof an airplane wing.

Figure 2 is an exploded view of the device in perspec tive showing thefore and aft fairings removed.

Figure 3 is a fragmentary view showing a snap or detent adapted to holdthe fairings in place.

Figure 4 is a perspective view of the device as it would appear when arocket has been fired and is leaving the device. t

Figure 5 is a cross-sectionalview taken on the line 5-5 of Figure 2.

Figure 6 isa longitudinal sectional view taken on the line 6-6 of Figure5. I a l Figure 7 is a fragmentary perspective view of the aft end ofthe device showing the structure and the rocket detents.

Figure 8 is a rear or aft end perspective view of one of the rockets.

Figure 9 is an exploded view showing the construction of the electricalactuated firing mechanism.

Figure 10 is a schematic view of the wiring circuit in one of its forms.

.Figure 11 is a wiring diagram applicable to the schematicrepresentation of Figure 10 in which representative values are shown.

Figure 12 is a-Wiring diagram of another form of the electrical circuitadapted to the firing of the rockets.

In an embodiment chosen to illustrate the invention.

there is shown a launching device comprising a body 10 l the body. isshown assembled with the fairings and occupying theposition it wouldhave with hangers 13 and 14 attached to a bomb rack or pylon 15.

The body construction is illustrated more particularly in Figures 2, 5and 6. As there shown it is constructed of a plurality of paper tubes16, six in number in the modification shown, grouped about a centraltube 17 of similar construction. It has been found advantageous toconstruct the paper tubes of spirally wrapped paper and preferablycoated on both the inside and the outside with a tough plastic. film,which film may be any one of a number of commercially available plasticmaterials which can be applied by customary coating processes.

In order that the, paper tubes may be anchored in their properpositions, there 'are provided a series of spacer blocks 18, preferablyof wood, which" are rounded to the same degree of curvature as theoutside surfaces further fix the positions ofthe tubes .16, outer-spacerlocation of.

blocks 19 are provided rounded on their inner sides where they areapplied against the exteriors of the tubes 16 and flat on the outer sideso that a wrapping 20 around the exterior of all of the tubes is kept assmooth-surfaced as possible in its substantially hexagonal form. In someforms of the device it has been found advantageous to employ a largeround paper or plastic tube for the exterior container encasing thesmall tube clustered as shown, even without the presence of spacerblocks or cradles.

To further assist in the proper placing and holding of the tubes 16 and17 there is provided a fore bulkhead 21 and an aft bulkhead 22. Thesebulkheads are preferably made of metal, steel being exceptionallyacceptable. The bulkheads are formed with flanged aperturescorresponding to the paper tubes and a flange 23 extending around theperimeter serving as a means for determining the shape of the exteriorof the body. Bulkheads 21 and 22 are similar to the extent that adescrip tion of one will suflice for both.

The hangers 13 and 14 are of a form heretofore found acceptable and inthe embodiment herein disclosed are fastened to the body by means ofscrews passed through the wrapping 20 into the blocks 19 on either sideof the uppermost of the tubes 16. When attached to the pylon 15 swaybraces 24 may be employed when necessary.

The fore fairing 11 is made of frangible material which may be of papiermache, pasteboard or craftboard, styrene impregnated or coated similarto the paper tubes with a plastic film on the inside and outside andmoreover painted especially on the outside so that the fairings conformto the body. To maintain the fairings in proper shape they are eachprovided with a reinforcing band 25 around the base which is crimpedover the outside and inside surfaces of the fairing. The body of thefairing 26 has a projectile-like shape curved in a general way so as tomatch the curve of a head 27 of a rocket 28.

In order to secure the fairing in each case to the body, the fairing isprovided with a series of three spring fasteners 29 (see Figure 3), eachof the spring fasteners being designed so that a beaded end 30 isadapted to snap into an aperture 31 of the body immediately behind theflange 23. The reinforcing band may also be provided with a series ofguide pins 32 adapted to fit into suitable holes 33 in the fore bulkheadat the edge to assist in the proper positioning of the fairing on thebody. When the fairing is guided into position on the body by insertionof the guide pins into the holes, the fairing is pushed firmly until thebeaded ends 30 fall into the apertures 31 at which time the fairing ishooked firmly in place. The fairing can, of course, be removed byspringing the beaded ends 30 out of position.

The rockets 28 herein shown and described serve primarily to illustratethe utility of the launcher which is equally effective for various typesof missiles.

The rockets 28 are identical and consist of a long cylindrical body atthe fore end of which is the head forming a continuation of the body andat the rear end of which is a series of four fins 41 as best shown inFigure 8, each fin having a mount 42 to which the fin is pivotallysecured by means of a pin 43. In Figure 8 the fins are shown folded inin the position they would have when inserted in the tubes 16 and 17 asappearing in Figure 6. The rockets have a rear face 44 at the edge ofwhich is an annular depression 45 of relatively shallow depth and havingsomewhat tapered walls.

For holding each rocket in place there is provided a spring-presseddetent 46 or detent latch, the form and mounting of which is perhapsbest illustrated in Figures 7 and 8. Each detent is constructed of anelongated spring member 4-7, one portion of which is anchored to theadjacent outer block 19 by suitable screws, the block 1 having a recess48 for reception of the elongated spring member. At the aft end of thespring member is a detent head 49 which is adapted to be received in ahole 50 in the paper tube 16, or 17, the outer block 19 being recessedat 51 for reception of the head.

The head is normally bent inwardly toward the interior of the tube andis constructed with opposite longitudinally disposed flanges 52 and 53having cut therein notches 54 and 55 so shaped that projections betweennotches may be received within the annular depression 45 which may betermed-a detent groove. The flanges furthermore are providedrespectively with bent-over portions 56 and 57 forming a smooth roundedcam-like exterior.

When the rocket is inserted fin or aft end first into the body and thetubes therein through the fore bulkhead, each rocket in turn is pushedinto the tube until the projections on the head of the detent fall intothe detent groove as illustrated in Figure 8. The spring force of thehead of the detent is sufiicient to anchor the rocket in place in itsrespective tube until the detent is overcome by the force of firing.

On occasions, however, it may become desirable to manually remove arocket from its tube. This is accomplished by rotating the rocket in thedirection of the arrow 58, for example. Rotation of the rocket willbring the next adjacent mount 42 into position against the near sidebent-over portion and pressure of the amount on the bent-over portionwill be sufiicient to cam the head 46 of the detent out of detentposition, after which the rocket may be freely withdrawn through thefore bulkhead.

The launcher is provided with an ignition assembly mounted on the aftbulkhead, this assembly being contained essentially within a housing 60to which it is attached by means of screws 61.

The housing, as illustrated in Figure 9, consists of a number ofparallel elements consisting of a plate 62 lying immediately adjacentthe bulkhead, an insulator plate 63, a second insulator plate 64, and acover plate 65, all of these plates being held together by the samescrews 61 already made reference to.

The plate 62 has a shield extension 66 extending laterally therefromdesigned to provide a protection for wiring from the initial blast ofthe rockets and also to provide means for attachment of a groundconnection.

The insulator plate 63 is illustrated as provided with suitable grooves67 designed to match comparable grooves in the plate 64. These groovesare for reception of an ignition spider 68. It is the ignition spiderwhich contains the means for ripple firing the rockets in accordancewith a predetermined sequence.

The ignition spider is illustrated schematically in Figure 10 and inthat modification consists of an electric circuit composed of a lead-inWire 69 adapted to connect to the rocket firing disc of the centerrocket at the point 70. A ground wire 71 connected at the point 72 to aground circuit 73 supplies the ground connection for all of the rocketsincluding the center rocket.

At a point 74 the lead-in wire is connected in one direction to a fuse75 which in turn is connected to the ground circuit 73. In anotherdirection contact is made at the point 74 with a resistance 76. From theresistance 76 connections are made respectively at point 77 to a fuse 78and a second resistance 79. Succeeding fuses are numbered 80, 81, 82, 83and 84. Succeeding resistances are numbered 85, 86, 87 and 88. Thelead-in wire 69 and ground wire 71 are designed to lie Within the shieldextension 66.

In the exploded view of Figure 9 the ignition spider, shownschematically in Figure 10, features the lead-in 69 as indicated, theground wire 71 as also indicated, the ground circuit 73, and the fuses75, 78, 80, etc., the resistances not being specifically illustrated inFigure 9. At the point 77, for example, and at corresponding succeedingpoints, connection is made to the respective rocket firing disc, thediscs being illustrated at the points in Figure 6. A plug connection89,;shown in Figure 1; is attached to the lead-in wire 69, the plugbeing adapted for connection to the circuit in the airplane. For readyidentificationthe firing mechanism may be referred to as anintervalometer directed to the launching of the missiles atpredetermined intervals.

For a more complete explanation of the firing mechanism of theintervalometer reference ismade to the wiring diagram of Figure 11. Inthat figure, for example, a

source of power is illustrated as originating in a twentyfour voltbattery 90, although it will be appreciated that an A. C. circuit is aseffective in this device as a D. C. circuit.

. In the circuit illustrated a time delay resistance 91 may be employedif need be to compensate for the current characteristics of the sourceof power. The rockets are numbered in sequence in Figure 11 beginningwith R1 indicating the center rocket and then respectively thesurrounding six rockets R2, R3, R4, R5, R6 and R7.

Valuesare given to the various resistances and fuses by way of exampleas being values which are operable when subjected to the source of powerof twenty-four volts. It will be noted that the internal firingresistance of a squib in the rocket in each instance. is one ohm. Eachof the seven fuses is provided with an identical resistance of .15 ohm.The resistances are each provided in the illustration with values of .4.ohm. For successful performance, however, there should be included afinal [resistance 92 having an arbitrary value greater than the the'lastrocket is to be fired for the timing to continue accurately, thereshould be a weighted resistance such as the resistance 92. I p

In the example illustrated it is assumed that a minimum of 0.5 amperewill be employed, although a current somewhere near half the averagecurrent of; and 1.5 amperes is more satisfactory in that it provides agreater margin of dependability. When contact is madeas by means of apush button 93, current is immediately connected to the rocket'Rl. Therocket, however, will be delayed in firing a small fraction of a secondsuflicient to have the current ignite the squib of the rocket. Currentwill be deflected to the rocket by the presence of the fuse 75 andresistance 76 and'the respective circuits in which they are connected.Upon the burning out of the squib in the rocket, current will thenfollow the path of least resistance and burn out the fuse 75. Theresistance of the fuse 75 is made such that it'will burn out at apredetermined-time interval which may be .01 second or some other choseninterval. After the fuse 75 has burned out, current will flow throughthe resistance 76 to the point 77 where again the major proportion ofthe current will be deflected to the firing squib of the rocket R2. Itwill be apparent thatthe delay in the firing of the rocket R2 is amatter of time'determined by the length of time required to burn out thefuse 75 plus the time required to ignite the squib in the rocket R2.Following the burning out of the squib in the rocket R2, current willthen be deflected through the fuse 78 until that is burned out in apredetermined time interval, after which the current will then passthrough the resistance 79 to the firing squib of rocket R3. Thisprogress of current continues through all of the fuses and all of theresistances except the resistance 92. Because of presence of theresistance 92, the last two rockets R6 and R7 will be fired at the sameprecise time interval rather than almost simultaneously as might be thecase should the resistance 92 be omitted. A regulated time interval ofripple firing is therefore assured and this interval can be veryaccurately controlled, at least sufiiciently accurately for properaiming and firing of the series of rockets by selection of fuses andresistances of properly balancedohm value. Inasmuch as most rockets arebuilt to a predetermined value of resistance in the firing squib,namely, approxi mately one ohm, the other values will be balancedaccordingly. f

In another more simplified form of the circuit illustrated in Figure 12,fuses have been dispensed withand the values of the resistances balanceto compensate for exclusion of the fuses. Again in this circuit theresistance of the firing squibs in the rocket is assumed to be one ohm.

In the modified circuit a source of power 100 is fed through aresistance 101 here selected as a resistance of five ohms. The currentfollows a lead-in wire 102 until it reaches a point 103 where it isadapted todivide, part of the current continuing to the point 104whereit is connected to the firing squib of rocket R1: A ground circuitelement 105' is connected to a ground circuit 105; a button 106 isdesigned to start the chain of firing.

In thisrform of the invention resistances 107, 108, 109, 110, 111 and112 have gradually increasing values, those values being illustrated onthe wiring diagram as .07 ohm increasing at increments of .02 ohm untilthe last resistance increment of .01 ohm. An end resistance 113 of .65ohm is provided, that resistance being slightly less than the sum of allof the preceding six resistances. The value of the end resistance 113 isselected so as to be substantially the equivalent of a continuation ofthe circuit. This assures firing of the last rocket in the samepredetermined sequence as those preceding it. .This may perhaps be morereadily appreciated when it isconsidered, for example, that theresistance of the'rocket R2 will become one ohm after rocket Rl is outof the circuit, having been fired. There need also be a compensatingfactor for rocket R2 and succeeding rockets due to a portion of thecurrent flowing into those rockets in quantities still insufficient tofire the respective rockets until the rocket immediately ahead of it inthe circuit is fired.

Of further importance in this form of the circuit is the fact that theresistances 107, 108, etc., can be made to very small values, namely,invalues of hundredths of an ohm increasing by increments of as littleas .02.ohm. By keeping these values small, a great many rockets morethan seven can be fired in the same accurate sequence by the same firingtechnique. The limit on the number of rockets thus fired runs intoseveral hundred before resistance values become too high to bepracticaL; At this point, however, additional rockets could be fired byrunning a lead-in wire 114 ina difierent direction to a new sequence ofrockets. The time interval between the firing of rockets with a circuitof this kind can be accurately controlled to intervals in theneighborhood of .040 second or at intervals shorter or longer than suchintervals. The time intervals can be further controlled to some degreeby the value of the current impulse sent into the system through thebutton 100.

It will therefore become apparent that a very accurate timing mechanismis possible by employment of extremely simple electrical structure andthe use of fuse and resistance elements of elementary character, thevalues of which can be readily determined and employed. Ignition spiderscan be made up following the scheme disclosed with a great degree ofeconomy without sacrifice of accuracy and dependability of timing. Suchignition spiders are readily insertable' in the ignition housing. Whereit may be desired to fire at a different ripple sequence, ignitionspiders having different sets of values can readily be replaced forthose removed. from thehousing.

Upon the firing of the initial rocket, the blast at the tail ports 115disintegrates the aft fairing 12 andas the rocket is propelled forwardthe nose 27 breaks through the fore fairing 11 at the center point undercircumstances where the center rocket is fired first. As the rocketvemerges from its tube, the fins 21 spring outwardly tearing open theremainder of the fairing 11 after which the 6 remaining rockets emergefrom the body in the sequence predetermined by the ignition spidervalues. After the last rocket has been fired, the body and thefragmented fairings can be jettisoned in the customary manner.

While we have herein shown and described our invention in what we haveconceived to be the most practical and preferred embodiment, it isrecognized that departures may be made therefrom within the scope of ourinvention, which is not to be limited to the details disclosed hereinbut is to be accorded the full scope of the claims so as to embrace anyand all equivalent devices.

Having described our invention herein, what we claim as new and desireto secure by Letters Patent is:

1. In a ripple firing multiple rocket launching device a body having acentral rocket tube and a plurality of rocket tubes distributedcircumferentially about the center, an aft bulkhead having tubeapertures therein coinciding one with each said tube, a circuit holderadapted to be secured to the outside face of the bulkhead between thecenter tube and the circumferentially disposed tubes, said holder beingsplit between forward and aft faces and having at least one adjacentface grooved for reception of a ripple firing wire circuit member, aripple firing wire circuit member comprising a direct wire connectionfor the central rocket, a ground circuit for all said rockets, a seriesresistance circuit for all said rockets having a connection for eachrocket, a separate series-connected resistance between each pair ofadjacent connections, and a fused circuit between each connection andthe ground including a fuse of lesser resistance than the adjacentresistance adapted to burn through at a predetermined time interval.

2. In an electric actuated ripple firing circuit for a series of rocketshaving resistance fired squibs therein of equal predetermined resistancevalues of a magnitude of about one ohm each, the combination of a sourceof electric power, a power line therefrom having a series of contactsfor the respective squibs, a ground from each squib, fusible connectionsfrom the respective contacts to the ground, continuous series connectedresistances between the respective contacts, said resistances havingvalues increasing at progressive increments of a relatively smallfraction of one ohm, and an end resistance greater than the sum of theresistance of the continuous resistances, the resistance value of saidresistances being balanced with the current value and the resistancevalue of the squibs whereby each squib is ignited at successive equalintervals after the firing of the preceding squib when the circuit isclosed to the source of electric power.

3. In an electric actuated ripple firing circuit for a series of rocketshaving resistance fired squibs therein of equal predetermined resistancevalues the combination of a source of electric power, a power linetherefrom having a series of contacts with the respective squibs, aground from each squib, fusible connections from the respective contactsto the ground of equivalent resistance values less than the resistancevalue of the squib, continuous series-connected resistances between therespective contacts, said resistances having equivalent values greaterthan the fusible connections, the resistance value of said fusibleresistances being balanced with the current value from the source ofelectric power, the resistance value of the continuous resistances andthe resistances of the squibs whereby the squibs are ignited atsuccessive equal intervals when the circuit is closed to the source ofelectric power.

4. In an electric actuated ripple firing circuit for a series of rocketshaving resistance fired squibs therein of equal predetermined resistancevalues the combination of a source of electric power, a power linetherefrom having a series of contact points for the respective squibs, aground from each squib, fusible connections from the respective contactpoints to the ground of equivalent resistance values less than theresistance value of the squib, continuous series connected resistancesbetween the respective contact points, said resistances havingequivalent values greater than the fusible connections and less than thesquibs, and an end resistance greater than the sum of the resistances ofthe fusible elements and continuous resistances, the resistance value ofsaid fusible resistances being balanced with the current value from thesource of electric power, the resistance value of the continuousresistances and the resistances of the squibs whereby the squibs areignited at successive equal intervals when the circuit is closed to thesource of electric power.

5. In a multiple rocket launching device comprising a body formed from aseries of tubes adapted for reception of rockets having tail fin mountsand a detent element adjacent thereto the combination of a rocket detentmeans in each tube of lesser detent strength than the rocket when underpower, said means comprising a spring member secured to the inside wallat the aft end of the tube, a head on the spring member free of directattachment to the tube and bent resiliently inwardly toward the centerof the tube, a longitudinally disposed flange adjacent the head having arocket-engaging detent element complementary to the detent element onthe respective rocket, a portion of said flange at the relative locationof the tail fin mounts having a laterally bent cam face adapted forcontact with and depression by one of said t ail fin mounts uponrotation of said rocket for manual release of the rocket.

6. In an expendable multiple rocket launching device comprising a bodyformed from a series of tubes adapted for reception of rockets havingtail fin mounts and an annular detent flange on each rocket adjacent themounts the combination of a rocket detent means in each tube of lesserdetent strength than the rocket when under power, said means comprisingan elongated spring member secured at its outer end to the inside wallof the tube at the aft end of the tube, a head at the inside end of thespring member free from direct attachment to the tube and bentresiliently inwardly toward the center of the tube, longitudinallydisposed flanges at the sides of the head each having a longitudinallyspaced flangeengaging notch therein, portions of said flanges at therelative location of the tail fin mounts having laterally bent cam facesadapted for contact with and depression by said tail fin mounts uponrotation of said mounts for manual release of the rocket.

References Cited in the file of this patent UNITED STATES PATENTS2,297,006 Lohrnan Sept. 29, 1942 2,458,476 Lauritsen J an. 4, 19462,496,316 Skinner et al. a Feb. 7, 1950 2,564,695 Johnson, Jr., et a1Aug. 21, 1951 2,609,730 Bergstrom Sept. 9, 1952 2,630,740 Robert et a1Mar. 10, 1953 2,736,260 Schlumberger Feb. 28, 1956 2,763,189 Grill Sept.18, 1956 FOREIGN PATENTS 863,443 France Jan. 2, 1941 62,297 Holland Dec.17, 1948

